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Symmetric airfoil geometry effects on leading edge noise

Symmetric airfoil geometry effects on leading edge noise
Symmetric airfoil geometry effects on leading edge noise
Computational aeroacoustic methods are applied to the modeling of noise due to interactions between gusts and the leading edge of real symmetric airfoils. Single frequency harmonic gusts are interacted with various airfoil geometries at zero angle of attack. The effects of airfoil thickness and leading edge radius on noise are investigated systematically and independently for the first time, at higher frequencies than previously used in computational methods. Increases in both leading edge radius and thickness are found to reduce the predicted noise. This noise reduction effect becomes greater with increasing frequency and Mach number. The dominant noise reduction mechanism for airfoils with real geometry is found to be related to the leading edge stagnation region. It is shown that accurate leading edge noise predictions can be made when assuming an inviscid meanflow, but that it is not valid to assume a uniform meanflow. Analytic flat plate predictions are found to over-predict the noise due to a NACA 0002 airfoil by up to 3 dB at high frequencies. The accuracy of analytic flat plate solutions can be expected to decrease with increasing airfoil thickness, leading edge radius, gust frequency and Mach number.
0001-4966
2669-2680
Gill, James
1e31eb24-f833-462e-b610-23b5b28e7285
Zhang, Xin
3056a795-80f7-4bbd-9c75-ecbc93085421
Joseph, Phillip F.
9c30491e-8464-4c9a-8723-2abc62bdf75d
Gill, James
1e31eb24-f833-462e-b610-23b5b28e7285
Zhang, Xin
3056a795-80f7-4bbd-9c75-ecbc93085421
Joseph, Phillip F.
9c30491e-8464-4c9a-8723-2abc62bdf75d

Gill, James, Zhang, Xin and Joseph, Phillip F. (2013) Symmetric airfoil geometry effects on leading edge noise. Journal of the Acoustical Society of America, 134 (4), 2669-2680. (doi:10.1121/1.4818769).

Record type: Article

Abstract

Computational aeroacoustic methods are applied to the modeling of noise due to interactions between gusts and the leading edge of real symmetric airfoils. Single frequency harmonic gusts are interacted with various airfoil geometries at zero angle of attack. The effects of airfoil thickness and leading edge radius on noise are investigated systematically and independently for the first time, at higher frequencies than previously used in computational methods. Increases in both leading edge radius and thickness are found to reduce the predicted noise. This noise reduction effect becomes greater with increasing frequency and Mach number. The dominant noise reduction mechanism for airfoils with real geometry is found to be related to the leading edge stagnation region. It is shown that accurate leading edge noise predictions can be made when assuming an inviscid meanflow, but that it is not valid to assume a uniform meanflow. Analytic flat plate predictions are found to over-predict the noise due to a NACA 0002 airfoil by up to 3 dB at high frequencies. The accuracy of analytic flat plate solutions can be expected to decrease with increasing airfoil thickness, leading edge radius, gust frequency and Mach number.

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Published date: October 2013
Organisations: Aeronautics, Astronautics & Comp. Eng

Identifiers

Local EPrints ID: 357454
URI: http://eprints.soton.ac.uk/id/eprint/357454
ISSN: 0001-4966
PURE UUID: cd88743a-6be1-42c9-a28e-24fd802a4f3b

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Date deposited: 08 Oct 2013 12:29
Last modified: 16 Dec 2019 20:29

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